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Pin for reducing relative rotational movement of disk and spacer of a turbine engine

A turbine engine, relatively rotating technology, applied in the direction of engine components, components of pumping devices for elastic fluids, engine manufacturing, etc., can solve problems such as reset imbalance, removal, etc.

Active Publication Date: 2022-04-29
SOLAR TURBINES
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

In order to reset the imbalance, the turbine engine may need to be removed for repair and disassembly

Method used

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  • Pin for reducing relative rotational movement of disk and spacer of a turbine engine
  • Pin for reducing relative rotational movement of disk and spacer of a turbine engine
  • Pin for reducing relative rotational movement of disk and spacer of a turbine engine

Examples

Experimental program
Comparison scheme
Effect test

Embodiment Construction

[0019] figure 1 A portion of an exemplary turbine engine 10 is shown generally in . Specifically, a cross-sectional view of the axial compressor 12 of the turbine engine 10 is shown. As will be appreciated by those skilled in the art, turbine engine 10 may also include combustors and power turbines and / or various additional or alternative components for compressing gases. Axial compressors 12 may include 1 A plurality of disc and spacer pairs 14 are oriented. Both disc and spacer pairs 14 may have similar configurations, therefore, only a single disc and spacer pair 14 will be described.

[0020] Each of the disk 16 and spacer 18 of the disk and spacer pair 14 may have a respective contact surface 20 , 22 that defines the engagement between the disk 16 and the spacer 18 . That is, at least some portions of the contact surface 20 of the disc 16 and at least some portions of the contact surface 22 of the spacer 18 may engage or connect to define an engagement. As used herei...

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PUM

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Abstract

An axial compressor (12) of a turbine engine (10) includes a plurality of disk and spacer pairs (14) oriented along a common axis of rotation. Each of the disk (16) and spacer (18) of the disk and spacer pair (14) has a contact surface (20, 22) that defines the engagement between the disk (16) and the spacer (18). The contact surface (20, 22) of each of the disc (16) and spacer (18) includes a recessed area (24, 26). The pin (28) has a stem (30) received in the recessed area (24) of the disc (16) and a head (32) received in the recessed area (26) of the spacer (18). The head (32) of the pin (28) includes at least two flats (40) corresponding to the complementary surfaces of the recessed area (26) of the spacer (18).

Description

technical field [0001] The present invention relates generally to turbine engines and, more particularly, to pins for reducing relative rotational motion of disks and spacers of an axial compressor of a turbine engine. Background technique [0002] Some axial compressors for turbine engines use spacers to provide internal flow passages for the working fluid. Spacers are typically thin rings mounted on each of the multiple disks of an axial compressor. Interference joints, or more specifically thermal interference joints and small cylindrical anti-rotation pins are used to couple each spacer to the respective disc. The disk and spacer pairs are oriented along a common axis of rotation of the axial compressor. During a hot shutdown of the turbine engine, the spacers typically cool and shrink at a higher rate than the corresponding disks, mitigating thermal interference bonding. The moment of inertia of the spacers often breaks the pins, allowing rotational displacement of t...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F01D5/06F01D5/32
CPCF01D5/066F05D2260/36F05D2250/13F05D2250/132F04D29/644F04D19/02F04D29/321
Inventor K·G·托马斯
Owner SOLAR TURBINES